Design of an Infrared Signature Suppressor for the Bell 205 (UH-1H) Helicopter Part II: Engine Flight Testing

摘要

This paper describes a design-test program to develop an Infrared Signature Suppressor for the Bell 205 helicopter. Through the use of computer prediction codes, and full-scale Hot Gas Wind Tunnel model testing, a prototype aerothermal design was established. This prototype has since been evaluated on a T53 engine test stand, and inflight on a Bell 205 helicopter. Details of the aerothermal design are presented in the companion paper "Part I -Aerothermal Design", submitted at the 7~* CASI Aerodynamics Symposium.